A numerical procedure has been developed for the prediction of the three-dimensional unsteady aerodynamic response of a helicopter rotor during self-generated blade-vortex interactions (BVI). Pertinent vortex wake parameters (e.g., spatial and temporal trajectories, strenghts) were computed using the lifting-line rotor/helicopter trim code CAMRAD/JA. In this code, tracking of the near-field BVI vortex-wake segments were accomplished using a new 'box' technique which involves tracking all tip vortex elements lying inside a user-specified box-like domain which encloses the rotor. Unsteady blade surface pressures were then predicted using a modified version (designated FPRBVI) of the full potential rotor code FPR (v 2.1). Two approaches were used to model vortex-induced effects in the FPRBVI solver; the efficient surface or 'transpiration' approach, and the more comprehensive split potential approach. The numerical procedure was used to predict the unsteady aerodynamic response of the one-seventh scale two-bladed AH-1G OLS model rotor and a United Technologies Corporation 17.5 % scale four-bladed model rotor during self-generated BVI. Accuracy of the numerical procedure was assessed using wind tunnel data.


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    Titel :

    A consistent approach for modeling the aerodynamics of self-generated rotor blade-vortex interactions


    Weitere Titelangaben:

    Ein konsistentes Verfahren zur aerodynamischen Modellierung von selbsterzeugten Rotorblatt-Wirbel-Interaktionen


    Beteiligte:
    Hassan, A.A. (Autor:in) / Charles, B.D. (Autor:in) / Tadghighi, H. (Autor:in) / Burley, C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1996


    Format / Umfang :

    11 Seiten, 10 Bilder, 24 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch